344 Federal Register / Vol. 79, No. 2 / Friday, January 3, 2014 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0811; Directorate 

Identifier 2008–NE–41–AD; Amendment 39– 

17715; AD 2013–26–06] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2010–19– 

01 for certain Rolls-Royce Corporation 

(RRC) AE 3007A series turbofan 

engines. AD 2010–19–01 required 

removing certain high-pressure turbine 

(HPT) stage 2 wheels, or performing 

inspections on them, and reduced their 

approved life limits. This new AD 

clarifies the AE 3007A turbofan engine 

model applicability, further reduces the 

approved life limits of affected HPT 

stage 2 wheels, and eliminates the 

inspections required by the existing AD. 

This AD was prompted by additional 

analysis that concluded that lower life 

limits for the affected HPT stage 2 

wheels are necessary. We are issuing 

this AD to prevent uncontained failure 

of the HPT stage 2 wheel, damage to the 

engine, and damage to the airplane. 

DATES: This AD is effective February 7, 

2014. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce Corporation, 450 South Meridian 

Street, Mail Code NB–01–06, 

Indianapolis, IN 46225, phone: 317– 

230–1667; email: CMSEindyOSD@rollsroyce.com; Internet: www.rollsroyce.com. You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2009– 

0811; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Kyri 

Zaroyiannis, Aerospace Engineer, 

Chicago Aircraft Certification Office, 

Small Airplane Directorate, FAA, 2300 

E. Devon Ave., Des Plaines, IL 60018; 

phone: 847–294–7836; fax: 847–294– 

7834; email: kyri.zaroyiannis@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2010–19–01, 

Amendment 39–16429 (75 FR 57660, 

September 22, 2010), (‘‘AD 2010–19– 

01’’). AD 2010–19–01 applied to the 

specified products. The NPRM 

published in the Federal Register on 

August 8, 2013 (78 FR 48339). The 

NPRM proposed to clarify the AE 3007A 

turbofan engine model applicability, 

further reduce the approved life limits 

of affected HPT stage 2 wheels, and 

eliminate the inspections required by 

the existing AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Clarify Applicability 

One commenter indicated that the 

compliance section may lead the 

operator to remove all engines with HPT 

stage 2 wheels, part number (P/N) 

23074462, while only a few engines are 

affected. He noted that compliance 

paragraphs in previous ADs on HPT 

stage 2 wheels used tables to identify 

affected and non-affected wheels. 

We do not agree. The applicability 

section of this AD states that the AD 

applies to RRC AE 3007A, A1, A1/1, 

A1/2, A1/3, A1P, A1E, and A3 turbofan 

engines with an installed HPT stage 2 

wheel, P/N 23084520 or P/N 23069438, 

23069592, 23074462, 23074644, or 

23075345, except for the HPT stage 2 

wheel serial numbers listed in Table 2 

through Table 5 of RRC Alert Service 

Bulletin (ASB) No. AE 3007A–A–72– 

414, Revision 1, dated December 5, 

2012. Therefore, as noted in the AD, 

operators do not need to remove engines 

with HPT stage 2 wheels, P/N 23074462 

with the serial numbers listed in Table 

2 through Table 5 of this ASB. We did 

not change this AD. 

Request Not To Reduce Life Limits 

One commenter indicated that eddy 

current inspections (ECIs) or surface 

wave ultrasonic test (SWUT) 

inspections of the HPT stage 2 wheels 

have proven satisfactory to this point as 

there have been no failures of engines in 

service worldwide. The commenter 

noted that reducing the life limit for 

these HPT stage 2 wheels is not 

justified. 

We do not agree. Per FAA risk 

guidelines as published in Advisory 

Circular (AC) No. 39–8 ‘‘Continued 

Airworthiness Assessments Of 

Powerplant And Auxiliary Power Unit 

Installations Of Transport Category 

Airplanes,’’ dated September 8, 2003 

(online at http://www.faa.gov/

documentLibrary/media/Advisory_

Circular/AC39-8.pdf), we do not rely on 

recurring inspections to serve as a final 

corrective action unless there is no 

practicable alternative. In this case, 

analysis and testing performed on the 

affected wheels by RRC has shown that 

the life limit for the affected wheels 

must be reduced. We did not change 

this AD. 

Request Not To Issue AD 

The same commenter noted that 

reduced life limits are already required 

based on an ASB published by RRC and 

incorporation of these life limits in the 

new RRC Engine Maintenance Manual 

(EMM), dated January 20, 2013. 

Operators have to consider these 

updates in their own maintenance 

programs. Therefore, an AD is not 

necessary. 

We do not agree. Companies cannot 

mandate that operators follow new life 

limits. AD compliance is mandatory. We 

did not change this AD. 

Request To Revise the Cost of 

Compliance Estimate 

The same commenter requested that 

the FAA include the number of aircraft 

affected worldwide in its cost of 

compliance estimate. He also indicated 

that cost of compliance should include 

an estimated labor cost of $250 per 

engine for each HPT stage 2 wheel 

change. 

We do not agree. First, our ADs apply 

only to U.S. registered or operated 

products, not to products registered 

elsewhere. Therefore, costs to operators 

registered elsewhere are speculative. 

Second, our cost estimate in this AD 

is based on the pro-rated cost of the 

reduction in life to the wheel. The labor 

cost of replacing the wheel is the same 

as it would be if the life of the wheel 

had not been changed. We did not 

change this AD. 


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Federal Register / Vol. 79, No. 2 / Friday, January 3, 2014 / Rules and Regulations 345 

Request To Continue Inspections and 

Related Compliance Issues 

The same commenter suggested 

revising the compliance section of this 

AD by continuing with ECIs and/or 

SWUT inspections at the interval 

required by AD 2010–19–01 (75 FR 

57660, September 22, 2010) or if the 

inspections are not performed at the 

required interval, then (1) the new life 

limit published in the RRC EMM, dated 

January 20, 2013, shall be considered; 

(2) at the next engine shop visit or when 

the life limit is reached, the affected 

parts will be changed; and (3) no engine 

can be released from an engine shop 

with life limits that exceed those 

published in the RRC EMM, dated 

January 20, 2013. 

The commenter asked that if this 

change cannot be accepted, then RRC 

should be required to lend an engine to 

the operator free of charge and change 

the HPT wheels free of charge. 

The commenter also indicated that 

providing a grace period of 15 cycles in 

service before removal of the engine for 

an issue that has been known and 

managed for the last 5 years without 

incident is not justified. 

We do not agree. Repetitive 

inspection of the affected HPT wheels is 

not a replacement for reduction in their 

life limit. As stated above, based on 

FAA risk guidelines as published in AC 

39–8, we do not rely on recurring 

inspections to serve as a final corrective 

action unless there is no practicable 

alternative. In the case of these affected 

wheels, analysis has shown that the life 

of these wheels must be reduced. 

Second, requests for warranty support, 

i.e., that RRC provide a free lease engine 

and free replacement HPT stage 2 wheel 

are economic issues between the 

operator and the original equipment 

manufacturer. Third, successful 

performance of a part has no effect on 

the need to remove that part once it has 

reached its life limit. However, we are 

providing a 15-cycle allowance to 

minimize disruptions to operators. This 

grace period is supported by our risk 

assessment. We did not change this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 18 

engines installed on airplanes of U.S. 

registry. We also estimate that a 

replacement HPT stage 2 wheel costs 

about $145,524, and that it will be 

replaced during an engine shop visit at 

no additional labor cost. Based on these 

figures, we estimate the total cost of the 

AD to U.S. operators to be $2,619,432. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2010–19–01, Amendment 39–16429 (75 

FR 57660, September 22, 2010) and 

adding the following new AD: 

2013–26–06 Rolls-Royce Corporation 

(Formerly Allison Engine Company): 

Amendment 39–17715; Docket No. 

FAA–2009–0811; Directorate Identifier 

2008–NE–41–AD. 

(a) Effective Date 

This AD is effective February 7, 2014. 

(b) Affected ADs 

This AD supersedes AD 2010–19–01, 

Amendment 39–16429 (75 FR 57660, 

September 22, 2010). 

(c) Applicability 

This AD applies to the following RollsRoyce Corporation (RRC) AE 3007A, A1, 

A1/1, A1/2, A1/3, A1P, A1E, and A3 turbofan 

engines: 

(1) With an installed high-pressure turbine 

(HPT) stage 2 wheel, part number (P/N) 

23084520, or 

(2) With an installed HPT stage 2 wheel, 

P/N 23069438, 23069592, 23074462, 

23074644, or 23075345, except for the HPT 

stage 2 wheel serial numbers listed in Table 

2 through Table 5 of RRC Alert Service 

Bulletin (ASB) No. AE 3007A–A–72–414, 

Revision 1, dated December 5, 2012. Those 

HPT stage 2 wheels maintain their existing 

approved life limits. 

(d) Unsafe Condition 

This AD was prompted by additional 

analysis that concluded that lower life limits 

for the affected HPT stage 2 wheels are 

necessary. We are issuing this AD to prevent 

uncontained failure of the HPT stage 2 wheel, 

damage to the engine, and damage to the 

airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For HPT stage 2 wheels, P/N 23069438 

and P/N 23069592, do the following: 

(i) For HPT stage 2 wheels that have 9,500 

cycles since new (CSN) or more on the 

effective date of this AD, remove the HPT 

stage 2 wheel from service within 15 cyclesin-service (CIS) after the effective date of this 

AD. 

(ii) After the effective date of this AD, do 

not approve for return to service any engine 

with an HPT stage 2 wheel, P/N 23069438 or 

P/N 23069592, that exceeds the new life limit 

of 9,500 CSN. 

(2) For HPT stage 2 wheels, P/N 23074462, 

do the following: 

(i) For AE 3007A1E turbofan engines with 

HPT stage 2 wheels installed that have 7,500 


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346 Federal Register / Vol. 79, No. 2 / Friday, January 3, 2014 / Rules and Regulations 

CSN or more on the effective date of this AD, 

and for the AE 3007A, A1, A1/1, A1/2, A1/ 

3, A1P, and A3 turbofan engines with HPT 

stage 2 wheels installed that have 9,500 CSN 

or more on the effective date of this AD, 

remove the wheel from service within 15 CIS 

after the effective date of this AD. 

(ii) Thereafter: 

(A) Do not approve for return to service 

any AE 3007A1E turbofan engine with an 

HPT stage 2 wheel, P/N 23074462, installed, 

that exceeds the new life limit of 7,500 CSN; 

and 

(B) Do not approve for return to service any 

AE 3007A, A1, A1/1, A1/2, A1/3, A1P, and 

A3 turbofan engines with an HPT stage 2 

wheel, P/N 23074462, installed, that exceeds 

the new life limit of 9,500 CSN. 

(C) Throughout the life of the HPT stage 2 

wheel, always use the lowest life limit 

applicable to any engine model in which the 

part was used in service. If life usage records 

are not sufficient to identify all engine 

models in which the part has been flown, the 

lowest life applicable to any engine model for 

which the part is eligible must be used. 

(3) For HPT stage 2 wheels, P/N 23074644 

and P/N 23075345, do the following: 

(i) For HPT stage 2 wheels that have 9,500 

CSN or more on the effective date of this AD, 

remove the HPT stage 2 wheel from service 

within 15 CIS after the effective date of this 

AD. 

(ii) Thereafter, do not approve for return to 

service any engine with an HPT stage 2 

wheel, P/N 23074644 or P/N 23075345, 

installed, that exceeds the new life limit of 

9,500 CSN. 

(4) For HPT stage 2 wheels, P/N 23084520, 

do the following: 

(i) For HPT stage 2 wheels that have 23,000 

CSN or more on the effective date of this AD, 

remove the HPT stage 2 wheel from service 

before the next flight after the effective date 

of this AD. 

(ii) Thereafter, do not approve for return to 

service any engine with an HPT stage 2 

wheel, P/N 23084520, installed, that exceeds 

the new life limit of 23,000 CSN. 

(f) Alternative Methods of Compliance 

The Manager, Chicago Aircraft 

Certification Office, may approve alternative 

methods of compliance for this AD. Use the 

procedures 14 CFR 39.19 to make your 

request. 

(g) Related Information 

(1) For more information about this AD, 

contact Kyri Zaroyiannis, Aerospace 

Engineer, Chicago Aircraft Certification 

Office, Small Airplane Directorate, FAA, 

2300 E. Devon Ave., Des Plaines, IL 60018; 

phone: 847–294–7836; fax: 847–294–7834; 

email: kyri.zaroyiannis@faa.gov. 

(2) RRC ASB No. AE 3007A–A–72–414, 

Revision 1, dated December 5, 2012, which 

is not incorporated by reference in this AD, 

can be obtained from RRC, using the contact 

information in paragraph (g)(3) of this AD. 

(3) For service information identified in 

this AD, contact Rolls-Royce Corporation, 

450 South Meridian Street, Mail Code NB– 

01–06, Indianapolis, IN 46225, phone: 317– 

230–1667; email: CMSEindyOSD@rollsroyce.com; Internet: www.rolls-royce.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(h) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

December 17, 2013. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2013–30734 Filed 1–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2013–0033; Airspace 

Docket No. 13–AEA–1] 

Establishment of Class E Airspace; 

Leesburg, VA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes Class 

E Airspace at Leesburg, VA, creating 

controlled airspace to aid Potomac 

TRACON in the safe and orderly flow of 

air traffic at Leesburg Executive Airport. 

This action enhances the safety and 

management of Instrument Flight Rules 

(IFR) operations at the airport. This 

action also updates the geographic 

coordinates of the airport. 

DATES: Effective 0901 UTC, February 6, 

2014. The Director of the Federal 

Register approves this incorporation by 

reference action under title 1, Code of 

Federal Regulations, part 51, subject to 

the annual revision of FAA Order 

7400.9 and publication of conforming 

amendments. 

FOR FURTHER INFORMATION CONTACT: John 

Fornito, Operations Support Group, 

Eastern Service Center, Federal Aviation 

Administration, P.O. Box 20636, 

Atlanta, Georgia 30320; telephone (404) 

305–6364. 

SUPPLEMENTARY INFORMATION: 

History 

On April 8, 2013, the FAA published 

in the Federal Register a notice of 

proposed rulemaking to establish Class 

E airspace at Leesburg, VA (78 FR 

20846) Docket No. FAA–2012–0033. 

Interested parties were invited to 

participate in this rulemaking effort by 

submitting written comments on the 

proposal to the FAA. No comments 

were received. Subsequent to 

publication the FAA found that the 

geographic coordinates of the airport 

were transposed. This action makes the 

correction. Class E airspace designations 

are published in paragraph 6002 of FAA 

Order 7400.9X dated August 7, 2013, 

and effective September 15, 2013, which 

is incorporated by reference in 14 CFR 

71.1. The Class E airspace designations 

listed in this document will be 

published subsequently in the Order. 

The Rule 

This amendment to Title 14, Code of 

Federal Regulations (14 CFR) part 71 

establishes the Class E airspace 

extending upward from the surface 

within a 6-mile radius at Leesburg 

Executive Airport, providing the 

controlled airspace required to aid 

Potomac TRACON in the safe and 

orderly flow of air traffic at Leesburg, 

VA. Also, the geographic coordinates of 

the airport are adjusted to coincide with 

the FAA’s aeronautical database. 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current, is non-controversial and 

unlikely to result in adverse or negative 

comments. It, therefore, (1) is not a 

‘‘significant regulatory action’’ under 

Executive Order 12866; (2) is not a 

‘‘significant rule’’ under DOT 

Regulatory Policies and Procedures (44 

FR 11034; February 26, 1979); and (3) 

does not warrant preparation of a 

Regulatory Evaluation as the anticipated 

impact is so minimal. Since this is a 

routine matter that only affects air traffic 

procedures and air navigation, it is 

certified that this rule, when 

promulgated, does not have a significant 

economic impact on a substantial 

number of small entities under the 

criteria of the Regulatory Flexibility Act. 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

Subtitle I, Section 106 describes the 

authority of the FAA Administrator. 

Subtitle VII, Aviation Programs, 

describes in more detail the scope of the 

agency’s authority. This rulemaking is 

promulgated under the authority 

described in Subtitle VII, Part A, 

Subpart I, Section 40103. Under that 

section, the FAA is charged with 

prescribing regulations to assign the use 

of airspace necessary to ensure the 

safety of aircraft and the efficient use of 

airspace. This regulation is within the 

scope of that authority as it establishes 

controlled airspace at Leesburg 

Executive Airport, Leesburg, VA. 


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